CN102177067A

CN102177067A - Rear part of an aircraft comprising a structure for supporting engines, extending through the fuselage and connected thereto by at least one connecting rod

Info

Publication number: CN102177067A
Application number: CN2009801405869A
Authority: CN
Inventors: 劳伦特·拉丰; 弗雷德里克·茹尔纳德; 德尔菲娜·贾尔伯特; 艾蒂安·巴杜
Original assignee: Airbus Operations GmbH
Current assignee: Airbus Operations GmbH
Priority date: 2008-09-18
Filing date: 2009-09-16
Publication date: 2011-09-07
Anticipated expiration: 2029-09-16
Also published as: FR2935954A1; EP2334556B1; RU2496684C2; US20110226894A1; FR2935954B1; CN102177067B; RU2011115010A; JP5467108B2; BRPI0918643A2; US8366040B2; CA2736777C; EP2334556A1; JP2012502846A; WO2010031959A1; CA2736777A1

Abstract

The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), extending through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means connecting the structure (14) to the fuselage (6), with first connection means connecting the structure to a first casing (50) forming the first opening (18) and second connection means connecting the structure to a second casing (50) forming the second opening (18). According to the invention, the connection means also comprise at least one effort recovery connecting rod (66), the first end of which is mounted on the structure (14) and the opposite end is mounted on the fuselage, at a distance from the first and second openings.

Description

Comprise the aircraft rear portion of structure that is used to support driving engine that runs through fuselage and be connected to fuselage by at least one pipe link

Technical field

The present invention relates generally to a kind of rear portion of aircraft, and this aircraft is equipped with the driving engine that is anchored on its fuselage.

Background technology

In order to make this rear portion aircraft part, propose between fuselage and each driving engine, to insert attached pole in the prior art.In this structure, pole directly is fixed on the fuselage.In order to ensure the satisfactory transmission of prime power towards fuselage, the fuselage part of pole, support pole and the securing device that is inserted between these elements need sizable size.This is equivalent to resistance, its deterioration the whole aeroperformance of aircraft.

Other solution comprises the supporting construction that is used for driving engine of the inner space that the aircraft that passes fuselage and limited by described fuselage is provided.At this level place of running through the passage of structure, utilize a plurality of bolts or similar clamp structure that this is run through structural engagement in fuselage through two fuselage opening.

Yet, guide to application force in the fuselage although this solution can reduce each place in two openings a little with respect to the above-mentioned solution intensity of the application force of the direction orientation of supporting construction---particularly along---, the opening frame still keeps local load.Cause being provided with the assembly of oversized dimensions like this---particularly opening frame and fuselage part on every side, thus impair the total mass of aircraft.

Summary of the invention

Therefore, the objective of the invention is to propose a kind of rear portion that solves at least in part about the aircraft of the above-mentioned shortcoming of prior art embodiment.

For this reason, the present invention relates to a kind of rear portion of aircraft, it comprises:

-fuselage, it defines the interior zone of aircraft;

-at least two driving engines;

-be used for the supporting construction of driving engine, it passes described fuselage at first opening and second opening part, described first opening and second opening are formed in the described fuselage and are distributed on the both sides of vertical mid-plane of aircraft, and described supporting construction has first and second opposed ends;

One of them described driving engine is outwards given prominence to and support to described first and second opposed ends of-supporting construction from fuselage respectively separately on the both sides of described vertical mid-plane; And

-described supporting construction is connected to the securing device of fuselage, it comprises described structure is connected to first securing device of first frame that forms described first fuselage opening and second securing device that described structure is connected to second frame that forms described second fuselage opening.

According to the present invention, securing device comprises that also at least one application force recovers (effort recovery) pipe link, the first end that described application force recovers pipe link is installed on the described supporting construction, and the described application force opposed end that recovers pipe link is installed on the fuselage and spaced apart with first opening and second opening.

Therefore, innovative design proposed by the invention advantageously can make the intensity of force that passes the fuselage opening frame minimize, thereby allows the fuselage opening frame to have the less size of comparing with the size of before having seen.In fact, no longer utilize the opening frame of fuselage, but through the distinctive pipe link of the present invention, so its first purpose is to introduce prime power at fuselage with the isolated point of opening place from driving engine and towards a part of power of fuselage orientation.Therefore, make the interior stress concentration of opening frame of fuselage minimize basically.

In addition, in order to make the stress concentration in the supporting construction of driving engine minimize at the fuselage opening place, preferably make the head rod end also be installed on this supporting construction and leave opening.Therefore the structure of less local pressure can have less size, the quality saving that is used to can not ignore.

Preferably, observe along the longitudinal direction of aircraft, described application force recovers the vertical direction inclination of pipe link with respect to aircraft.Allow its transmission power on following direction like this, that is: at least one component is in the directed in a lateral direction direction of aircraft.In fact, it is the most difficult utilizing first securing device be contained in the fuselage opening and second securing device to recover these transverse forces, thereby makes that the aforementioned orientation of described pipe link is corresponding with practical problems.

Preferably, two application forces are set recover pipe link, two application forces recover pipe link and arrange symmetrically about the described vertical mid-plane of aircraft.The symmetry that is realized advantageously allows the compensation to a certain degree in the process motive recovery of pipe link, and this pipe link preferably is arranged in the Transverse plane of aircraft, but alternately can be with respect to this plane inclination.In addition, pipe link more than two can be set under the situation that does not exceed scope of the present invention.

Preferably, described supporting construction forms V-arrangement basically, and described two application forces recovery pipe link forms together basically with respect to the inverted V-arrangement of the V-arrangement of described supporting construction.

Preferably, the described opposed end of two pipe links is installed in the same point on the fuselage basically, and described point belongs to the described vertical mid-plane of aircraft.Naturally, under the situation that does not exceed scope of the present invention, they can be installed in two difference places of fuselage.

Preferably, each application force recovers pipe link in the hinged installation in its end.

Preferably, each application force recovers the top that pipe link is installed in described supporting construction, but also it is contemplated that the position relative with it.

Preferably, in order to filter/damped vibration, at least one application force recovers pipe link and is equipped with syntonizer.

Preferably, described at least two application forces recover pipe link and are arranged to onboard hingedly, and plate itself is hinged on the supporting construction or on the fuselage.Make the application force that can balance transmits like this by each pipe link.

Preferably, described supporting construction is configured to by the first half hitch structure and second half hitch of described first opening that passes fuselage respectively and second opening, and the described first half hitch structure and the second half hitch structure are assembled each other and made them to dismantle in described interior zone.

Therefore, make the assembly and disassembly operation of the supporting construction can greatly help driving engine like this because now its by reversibly each other two independent half hitch structures of stack-mounted finish.Therefore each in these two described half hitch structures can be independent of another and operates in assembling/unloading process, thereby makes work more easy for the operator.Particularly, in initial stack-mounted process and in the replacing process in supporting construction, each supports the half hitch structure only need pass single fuselage opening, and this advantageously has significant simplification for the operator.

In addition, in the assembly operation process, each described half hitch structure can be equipped with its driving engine at its place, end before inserting its corresponding fuselage opening, be then assembled to second half structure.This has also further simplified assemble method with respect to the solution of the single structure of previous use, because under the situation of the solution of single structure, only just powerplant module can be installed on this structure after placing this structure on the fuselage.

Naturally, suppose that each driving engine can place when maintaining attached even in its support half hitch structure that is associated, so from the process of driving engine dismounting supporting construction, also can observe an advantage on this.

At last, another advantage that is produced by the embodiment with two described half hitch structures is that when observing them from the front portion, they can relative to each other tilt, and particularly makes them form V-arrangement.

Yet, under the situation that does not exceed scope of the present invention, can consider the supporting construction that runs through of two openings making by single and pass fuselage.

In the nonrestrictive detailed description below, it is obvious that other features and advantages of the present invention will become.

Description of drawings

Finish this explanation with reference to the accompanying drawings, in the accompanying drawing:

-Fig. 1 shows the three-dimensional sketch according to the aircraft rear portion of a preferred embodiment of the present invention;

-Fig. 2 shows the more detailed view of the cross-sectional plane of aircraft rear portion shown in Figure 1, has intentionally omitted the supporting construction that is used for driving engine and has been fastened to device on the fuselage;

-Fig. 2 a illustrates the assemble method that is used for the rear portion shown in the earlier drawings;

-Fig. 3 illustrates view like the view with Fig. 2, the supporting mechanism that is used for driving engine shown in this figure is fastened on first securing device and second securing device on the frame that forms fuselage opening, described first securing device and second securing device adopt the form of first embodiment, and this figure is also corresponding to the cross sectional drawing along the vertical curve III-III of Fig. 4;

-Fig. 3 a shows first replacement scheme of structure shown in Figure 3;

-Fig. 3 b shows second replacement scheme of structure shown in Figure 3;

-Fig. 4 shows along the cross sectional drawing of the vertical curve IV-IV of Fig. 3;

-Fig. 5 shows view like the view with Fig. 3, and the supporting construction of driving engine is made according to alternative embodiments in the figure;

-Fig. 6 shows view like the view with Fig. 3, and described in the figure first securing device and second securing device adopt the form of second embodiment, and this figure is also corresponding to the cross sectional drawing along the vertical curve VI-VI of Fig. 7;

-Fig. 7 shows along the cross sectional drawing of the vertical curve VII-VII of Fig. 6;

-Fig. 8 is the block diagram that Fig. 6 and shown in Figure 7 first supports the half hitch structure;

-Fig. 9 shows view like the view with Fig. 6, and described in the figure first securing device and second securing device adopt the form of the 3rd embodiment, and this figure is also corresponding to the cross sectional drawing along the vertical curve IX-IX of Figure 10;

-Figure 10 shows along the cross sectional drawing of the vertical curve X-X of Fig. 9;

-Figure 11 shows the cross sectional representation of one of them blocking element that belongs to the Fig. 9 and first securing device shown in Figure 10; And

-Figure 12 shows the cross sectional representation of one of them second damping member that belongs to the Fig. 9 and first securing device shown in Figure 10.

The specific embodiment

Fig. 1 shows the rear portion 1 of the aircraft of the form that adopts a preferred embodiment of the present invention.

In whole the following describes, by convention, X refers to the longitudinal direction of aircraft, and it is parallel to the longitudinal axis 2 of this aircraft.Y refers to the direction with respect to the aircraft transversal orientation, and Z refers to vertical direction or height, and these three direction X, Y and Z are perpendicular to one another.

In addition, proal direction considered that this direction is schematically illustrated by arrow 4 after term " preceding " and " back " should be subjected to the thrust that applied by driving engine with respect to aircraft.

Generally speaking, rear portion 1 comprises fuselage 6, and this fuselage 6 has circular basically, oval or similar cross-sectional plane, has the center of passing longitudinal axis 2, and defines the interior zone of aircraft 8.

In addition, it comprises at least two driving engines 10, and these at least two driving engines 10 are arranged on the either side of the vertical mid-plane P that passes through axis 2.In a preferred embodiment, be provided with on the wherein side that 10, one driving engines of two driving engines are positioned at fuselage 6, these driving engines generally can be turbojet, propeller turbine or other type.In these driving engines each all has the longitudinal axis 12 that is arranged essentially parallel to direction X.

In order to ensure suspending of these driving engines, be provided with supporting construction 14, this supporting construction 14 preferably is arranged in the Transverse plane, and has and pass interior zone 8 and in two characteristics that opening part passes fuselage of fuselage.As shown in Figure 1, the edge of this structure 14 is laterally left plane P and is covered by aerodynamic force fairing 16 from the outwards outstanding part of fuselage.

More clearly, with reference to Fig. 2, can find out that first opening and second opening of supporting construction 14 in being formed at fuselage---all is labeled as 18---and locates to pass fuselage 6.These two openings 18 are distributed on the both sides of vertical mid-plane P, and with respect to vertical mid-plane P symmetric arrangement, this plane P also constitutes the symmetrical plane at the whole rear portion of aircraft basically.

Supporting construction 14 has first opposed end and second opposed end---and all be labeled as 20, one of them driving engine 10 is outwards given prominence to and support to each opposed end from fuselage respectively on the either side of plane P.

Therefore each end 20 is compared to attached pole 4 structures of rigidity, for example has to be equal to or to be similar to from the prior art known design, in order to the driving engine that suspends of face under the wings of an airplane, and therefore guarantees the transmission of motive structure towards aircraft.

In this preferred implementation, the supporting construction 14 of driving engine---all is labeled as 22---by the first half hitch structure and the second half hitch structure and makes, and passes first opening 18 and second opening 18 of fuselage respectively.

In addition, they are assembled each other and make them to dismantle in interior zone 8.For this reason, the first half hitch structure 22 has the inner end 24 relative with first end 20, and the second half hitch structure 22 has another inner end 24 relative with the second end 20, therefore two

inner ends

24,24 contact with each other and assemble and make them to dismantle in interior zone 8, for example, utilize bolt and/or safety pin (not shown).

Preferably, at fastening interface the plane P place finish two joints between the described

half hitch structure

22,22, plane P is passed bolt and/or pin thus.Usually, this plane P constitutes the symmetrical plane at the supporting construction of driving engine 14, observes from front as shown in Figure 2, and this supporting construction is the V-arrangement shape basically.

In fact, the first half hitch structure 22 in left side that is considered as being arranged in Fig. 2 is to extend towards the top and to tilt with respect to direction Y away from the mode of plane P, equally, be considered as being arranged in the second half hitch structure 22 on right side of Fig. 2 also to extend towards the top and to tilt with respect to direction Y away from the mode of plane P.Therefore, the first half hitch structure 22 is along extending with respect to direction Y and Z bevelled first direction 28a in Transverse plane, and simultaneously, the second half hitch structure 22 is along also extending with respect to direction Y and Z bevelled second direction 28b in same Transverse plane.

Each

half hitch structure

22,22 adopts the form of beam or box, and described half hitch structure its inner end 24 from be arranged in plane P extends to its

opposed end

20,20 that supports one of them driving engine 10 basically point-blank on its direction 28a that is associated, 28b.

In a preferred embodiment, the V-arrangement that is formed by structure 14 is towards upper shed, and its tip is arranged in the top of longitudinal axis 2.Because the positioning free at the tip of V-arrangement and the freedom of setting the angle value of V-arrangement, so that can adapt to existing different stress best, and the aerodynamics that particularly makes outer section place can being limited in

half hitch structure

22,22 best suffer ruptures.

When in fact, support structure designs become to make and to observe from the front at each half hitch structure:

Acute angle (V) between the horizontal mid-plane P ' of-fuselage and the line 32 is greater than 25 °, and described line 32 connects the axis 2 of fuselage and the longitudinal axis 12 of driving engine; And

-described half hitch structure along direction 28a, the 28b of its extension and at the passage place of described half hitch structure perpendicular to the acute angle (W) between the direction 34 of fuselage less than 20 °.

The relatively large value at this angle (V) makes can be with engine position at the height place with respect to the expectation of fuselage, for example engine axis 12 is arranged in the horizontal surface near the upper end of fuselage, simultaneously, the feasible existence that can exempt additional aerodynamic fairing of the value at less relatively angle (W)---it changes into the spacing between fuselage and each half hitch structure---.

Above-mentioned design allows assembly and disassembly supporting construction easily 14.In fact, Fig. 2 a with reference to the method that illustrates the rear portion 1 that is used to assemble aircraft, can find out that this method comprises the step that is used to place the first half hitch structure 22, that is: place under the situation in the place ahead of orientation movements direction 36a at the inner end 24 of the first half hitch structure 22, motion by the first half hitch structure 22 makes it pass first fuselage opening 18, the first direction 28a that this sense of motion 36a extends after for example in a single day installing corresponding to the described first half hitch structure.

Side by side or one after the other, enforcement is used to place the step of the second half hitch structure 22, that is: place under the situation in the place ahead of orientation movements direction 36b at the inner end 24 of the second half hitch structure 22, motion by the second half hitch structure 22 makes it pass second fuselage opening 18, the second direction 28b that this sense of motion 36b extends after for example in a single day installing corresponding to this second half hitch structure.

In each step in these two steps, driving engine 10 can be installed in (not shown among Fig. 2 a) on the outer end 20, so that simplify and shorten this assemble method.

In addition, make

inner end

24,24 be sized to pass their corresponding fuselage opening 18,18, preferably, when---for example rib or allied equipment---, also make

inner end

24,24 be sized to pass their corresponding fuselage opening 18,18 even when the stack-mounted intensifier that is used for two half hitch structures that is equipped with them.Alternately, only after

inner end

24,24 has passed

opening

18,18, just these intensifiers are installed on the

inner end

24,24.

Usually, under the situation in the middle opening plane, the ratio of the height of the height of opening and half hitch structure is between 1.3 and 2.In addition, in this identical plane, on directions X, the ratio of the degree of depth of the degree of depth of opening and half hitch structure is between 1.1 and 1.5.

Then, utilize preferably along the aforementioned connecting device of direction Y orientation inner end 24 and be assembled on the inner end 24 of the described second half hitch structure 22 the first half hitch structure 22.

Between the supporting construction of total time, airframe, and engine, be provided with securing device.

Fig. 3 and Fig. 4 show first preferred implementation.

These devices at first comprise first securing device that the first half hitch structure is connected to first frame that forms first fuselage opening, and second securing device that the second half hitch structure is connected to second frame that forms second fuselage opening.First securing device and second securing device have same basically design and about the plane P symmetry, will only describe first device below.

At first, should be pointed out that first opening 18---its have with the design of second opening 18 same or similar design---be utilize in passage among the fuselage skin 40a and another the relative passage formation among the outer fuselage skin 40b.These two passages form the outlet of the inlet and the opening 18 of opening 18 respectively.

Described opening is defined by forward fuselage framework 42 in front and is defined by another rear portion fuselage ring 42 in the back.As shown in Figure 4, other fuselage ring 42 between two aforesaid frame can cut so that present opening 18.In addition, opening in the above by on close crosspiece 44 and define, close the preferably whole thickness of extend through fuselage on directions X of crosspiece 44 on this, and it connects two forward fuselage frameworks and rear portion fuselage ring 42,42.Similarly, opening 18 below by under close crosspiece 46 and define, the preferably whole thickness of extend through fuselage on directions X of crosspiece 46 is closed in this time, and it connects two forward fuselage frameworks and rear portion fuselage ring 42,42.These four

elements

42,42,44,46 form first frame 50 that limits opening 18 together.

Therefore, in the perpendicular that the line IV-IV by Fig. 3 limits, as on the middle opening plane---its can be counted as perpendicular to half hitch structure 22 and basically between the outlet of the inlet of opening and opening in the middle of the place pass the plane of opening---in the same, its four faces 42 that frame 50 utilizations are limited respectively by

aforementioned components

42,42,44,46 ', 42 ', 44 ', 46 ' and present tetragonal form.In these identical planes, four faces of half hitch structure 22 also form quadrangle, and the face of half hitch structure is relative in twos with the face of opening.Therefore, the anterior face 52 of half hitch structure ' with the anterior face 42 of frame ' relative, the rear 52 of half hitch structure ' with the rear 42 of frame ' relative, the upper side 54 of half hitch structure ' with the upper side 44 of frame ' relative, the bottom surfaces 56 of half hitch structure ' with the bottom surfaces 46 of frame ' relative.

Guarantee first securing device that the first half hitch structure 22 is assembled on first frame 50 is at first comprised a plurality of bolts 53, this bolt 53 is substantially perpendicular to the direction 28a of half hitch structure 22 and is arranged among the YZ of plane, thus allow the upper side 44 of upper side 54 ' be hooked in frame ' on.Therefore, be provided with one or a plurality of bolts of arranging along isolated two the diverse location places of direction X at half hitch structure 22 with embarking on journey.Make like this and can guarantee in the YZ of plane along on the direction perpendicular to direction 28a---by 58,60 signals of two arrows---the recovery of application force.In other words, these bolts 53 make and can recover in the middle opening plane or the application force in the plane in parallel.

Similarly, first securing device comprises one or more bolts 61, and this bolt 61 is substantially perpendicular to the direction 28a of half hitch structure 22 and is arranged among one or more plane X Z, thus allow the anterior face 42 of anterior face 52 ' be hooked in frame ' on.Therefore, preferably, half hitch structure 22 is provided with bolt 61, makes can to guarantee in plane X Z along on the direction perpendicular to direction 28a---such as in Fig. 4 by arrow 62 signal---the recovery of application force.In other words, this bolt 61 also makes and can recover application force in mid-plane or plane in parallel, and more preferably recovers the application force on the direction X that bolt 61 extends.

Alternately, can be different from its anterior face 42 ' and upper side 44 ' on other mode half hitch structure 22 is pressed on the frame 50.In fact, preferably manage described half hitch structure 22 is pressed on two attachment surface of frame, therefore according to one of them replacement scheme, these two attachment surface can be bottom surfaces 46 ' and rear 42 '.

Preferably, each

bolt

53,61 or every capable bolt are arranged to form flexible fastener.

For example, this is by one or more damping members finishes---for example by the member of making such as the polymeric material of the elastically deformable of elastic body or rubber type---, thereby makes it can damped vibration and therefore participate in the isolation of fuselage and driving engine from the vibration aspect.Herein, this damping member preferably adopt the stack-mounted face 42 in twos of being squeezed in ', 52 ' and 44 ', 54 ' between the form of elastomer block 64 because described of tension application force and extruded mistake that draw power from introduce

bolt

53,61 is caused.Yet, although make that owing to this solution can obtain the vibration damping performance this solution is preferred, but alternately, under the situation that does not exceed scope of the present invention, can consider stack-mounted face 42 in twos ', 52 ' and 44 ', 54 ' between rigidity with directly contact.

Fig. 3 illustrates more clearly: finish first securing device and second securing device by the existence that the peculiar one or more application forces of the present invention recover pipe link.Make and the effect intensity of force that passes opening frame 50 can be minimized to have less size so generally thereby allow frame 50 to compare with the frame that had before run into.

In the illustrated embodiment, be provided with two pipe links 66 about the plane P symmetric arrangement.In these pipe links each has and is supporting first end or the bottom shown in the half hitch structure 22, and its opposed end or upper end are left opening 18 and be installed on the fuselage.

Owing to adopt symmetric mode,, that is: finish the pipe link of first securing device so will only describe the left pipe link 66 among Fig. 3.

In order to make the stress concentration in the support half hitch structure 22 at opening 18 places minimize, preferably, make the head rod end also be installed on this supporting construction in the mode of leaving opening, therefore preferably be in the inner space 8.This first end 8 preferably is hingedly mounted on the half hitch structure 22, for example utilizes the accessory 68 with its one.

It extends and close simultaneously vertically mid-plane P then, and its opposed end is installed on the fuselage in this vertical mid-plane, a part preferably mounted thereto as shown in the figure.Same herein, this connects radial type preferably, utilizes towards interior zone outstanding accessory 70 or fuselage ring extension.

Two application forces recover pipe links, and---it preferably is arranged in the Transverse plane and their opposed end is installed in the same point of the plane P of fuselage basically---forms the inverted V-arrangement with respect to the V-arrangement of supporting construction 14 together basically.

Yet, can be according to the position and the orientation of the demand change pipe link that is run into.From this on the one hand, pipe link can be arranged in structure 14 below, rather than as shown in the figure be arranged in structure 14 above.

Usually, preferably, along observing as the direction X among Fig. 3, each application force recovers pipe link 66 and tilts with respect to direction Z.Allow it along following direction transfer function power like this, that is: at least one component of this direction is along direction Y orientation.In fact, it is the most difficult utilizing first securing device that is contained in the fuselage opening 18 to recover these horizontal forces.

In the illustrated embodiment, each pipe link 66 tilts with respect to direction Y and Z basically, thereby rises when it extends towards the inboard.The application force of---two arrows 72 by Fig. 3 are illustrated---therefore recovers fully by securing device on these two pipe link directions then.Yet under the situation that does not exceed scope of the present invention, one of them alternative solution is along direction Y orientation with each pipe link 66.

A plurality of pipe links 66 as shown in Figure 3 can be set, so their quantity is not limited to one or two between supporting construction 14 and fuselage 6.In addition, damping strut member (damping jack) (not shown) of one or more pipe links vibration that can be sent to fuselage by decaying/filtering is respectively replaced.

Still---that is: the vibration that can be passed to fuselage in decay/filtration by pipe link 66 under---the situation, be equipped with syntonizer at least one that can be in them, Fig. 3 a shows the example of syntonizer in identical target.In the figure, syntonizer is provided in the end of the pipe link of the accessory 70 that is connected in fuselage 6.This syntonizer that extends vertically 150 comprises mallet portion 152, and this mallet portion 152 is connected to the pipe link end by its one of them end, simultaneously its other end support blocks 154.As schematically illustrated by the arrow 156 of Fig. 3 a, the decay that is passed to the vibration of fuselage by pipe link is that---that is---hunting motion: the link pin of the mallet portion on the accessory 70 is finished for link pin by the pipe link of block 154 on the accessory 70 of fuselage.

In addition, as mentioned above, can and limit the layout of revising pipe link 66 according to the demand that is run into.In Fig. 3 b, two pipe links 66 have outer end (not shown) and inner end respectively, this outer end is fastening, preferably be hinged on the fuselage, preferably on the lateral part of fuselage, this inner end is fastened on, is hinged on the plate 158, and plate 158 itself is hinged on the supporting construction 14, preferably in the middle.Therefore, the inner end of two pipe links 66 be connected plate preferably on the both sides of link pin 160 directed on the direction X, the application force of therefore can balance introducing by each pipe link 66.In addition, suppose its eliminated by have two pipe links that structure caused was indeterminate, so should help assembling by additional plate the earth.Fig. 3 b shows following structure, that is: the V-arrangement that forms by two pipe links 66 be downwardly facing opening and be arranged in supporting construction 14 generally below, but this is nonrestrictive.

Alternately, the plate 158 that connects two pipe link ends can be hinged on the fuselage, for example on the fuselage accessory 70 that is described about Fig. 3, rather than on supporting construction.

Fig. 5 shows following embodiment, wherein keeps aforesaid securing device, and only the supporting construction 14 of driving engine has different designs.In fact, supporting construction no longer is configured to by two half hitches secured to one another, but is made by the single structure that passes two

openings

18,18, this single structure preferably straight line with horizontal.Should be pointed out that and can use such structure, and irrelevant with the characteristic of selected securing device.Particularly, other preferred implementation of the securing device that will describe below it is applicable to.

Fig. 6 to Fig. 8 shows another preferred implementation, and in this embodiment, first securing device and second securing device adopt the form of second embodiment respectively, and stick effect power is recovered pipe link 66 herein.

In fact because first securing device is identical and symmetrical with second securing device, so first securing device will only be described, first securing device be included in now the rear 52 of half hitch structure 22 ' with the rear 42 of frame ' between radial type be connected.For this reason, the axle 80 that is parallel to direction 28a will connect respectively with relative face 42 ', 52 ' the yoke portion 82 and the accessory 84 that integrate, vice versa.Preferably, other face of half hitch structure 22 and frame 50 does not have connecting device, but still relative in couples.

The connection that is obtained guaranteed in the YZ of plane along on the direction perpendicular to direction 28a---such as by arrow 86 signal---application force recovery and in plane X Z on the direction of edge perpendicular to direction 28a---such as by arrow 88 signal---the recovery of application force.In other words,---preferably include as by the direction X shown in the arrow 88---recovers application force in middle opening plane or plane in parallel to be connected with this of axle 80 that make can be along the both direction that is perpendicular to one another.

Fig. 9 and Figure 10 show another preferred implementation, and in this embodiment, first securing device and second securing device adopt the form of the 3rd embodiment respectively, and also stick effect power is recovered pipe link 66 herein.

First securing device and second securing device have substantially the same design and about the plane P symmetry, will only describe first device below.

In the 3rd embodiment, first securing device at first comprises the blocking element (blocking element) of at least one supporting construction, bears clamp load when this blocking element is bearing on first frame 50 on the one hand and be bearing on the support half hitch structure 22 on the other hand.In this structure, first securing device utilizes blocking element to form at least in part, and this blocking element no longer is to work in traction as the situation in the traditional element of the bolt type of prior art or similar type working in the compression.Make like this to be easy to change these blocking elements,, and need not to pass frame 50 or support half hitch structure 22 because blocking element can be in the fuselage opening 18 fully.

Usually, Reference numeral is that each blocking element of 90,92 bears clamp load so that apply power on given of structure, cause like this with this given relative face to contact or non-contacting mode is bearing on the face relative with it of frame.Therefore, in the illustrated embodiment, blocking

element

90,92 is arranged to bear clamp load respectively on two independent directions, and is installed in the middle opening plane, is enough to like this keep half hitch structures 22 with respect to frame 50 on all directions of the mid-plane of fuselage opening.

More clearly, first securing device comprises blocking element schematically illustrated among Fig. 9 and Figure 10 90, these elements 90 that bear clamp load be bearing in the upper side 44 of the upper side 54 of half hitch structure ' go up and frame ' on.Therefore, be provided with one or a plurality of elements 90 of arranging along the isolated two or more different positions of direction X at half hitch structure 22 with embarking on journey.Make like this and can guarantee in the YZ of plane in recovery perpendicular to the application force on the direction of direction 28a.In other words, these blocking elements 90 make and can recover in the middle opening plane or the application force in the plane in parallel.

Similarly, first securing device is included in blocking element schematically illustrated among Figure 10 92, these elements 92 that bear clamp load be bearing in the rear 52 of half hitch structure ' and the rear 42 of frame ' between.Therefore, be provided with one or a plurality of elements 92 of arranging along the isolated two or more different positions of direction Z at half hitch structure 22 with embarking on journey.Make like this and can guarantee in plane X Z in recovery perpendicular to the application force on the direction of direction 28a.In other words, these blocking elements 92 also make and can recover in the middle opening plane or the application force in the plane in parallel, and more preferably recover the application force on direction X.

Herein, for the anterior face 42 that makes anterior face 52 ' press frame ' and for the bottom surfaces 46 that makes bottom surfaces 56 ' press frame ', with blocking

element

90,92 be arranged on rear 42 ' and upper side 44 ' on.Alternately, blocking

element

90,92 can be arranged on frame be different from rear 42 ' and upper side 44 ' face on.In fact, preferably, by the blocking element that will bear clamp load be arranged on anterior face 42 ' and bottom surfaces 46 ' on, manage this half hitch structure 22 is pressed on two attachment surface of frame, therefore according to one of them alternative method, these two attachment surface can be rear 42 ' and upper side 44 '.

As below describing in detail, it is flexible fastening that each blocking

element

90,92 or every units preferably are arranged to utilize damping member to form.

In addition, second damping

member

94,96 be inserted into other two attachment surface 42 of supporting half hitch structure and frame 50 ', 46 ' between.Second damping member makes and do not have direct contact between supporting construction and frame, even can expect this direct contact.When this damping member and second damping member are not set, so between supporting construction and frame, obtain so-called rigidity assembling.

Yet the situation in the embodiment as shown is the same, and each blocking element is bearing on the described supporting construction via damping member and/or on its frame that is associated.As mentioned above, so advantageously make to obtain certain flexibility, thereby reduce the vibration in the fuselage at first securing device and second securing device.In other words, preferably advantageously make can damped vibration for the damping member of being made by the polymeric material of the elastically deformable of for example elastic body or rubber type, and therefore participates in isolating the isolation of fuselage and driving engine from the vibration aspect.Same herein, alternately, can use other damping member of types of springs.

Figure 11 shows a possible embodiment at each blocking

element

90,92 that is combined with this damping element.

In the figure, show the member that blocking element 90 comprises bar 98 forms, this bar be oriented be substantially perpendicular to its bonded assembly face 44 ', 54 '.In the housing 100 of overhang bracket on being arranged at this face of face 54 ' synergistic this bar 98 of half hitch structure.In order to keep supporting better, this end that forms first area supported 101 can be crooked and have shape with the shape complementarity of housing 100.The upper side 44 of crosspiece 44 ' on, be provided with and hold for example housing 102 of the damping member 104 of the form of elastomer block.The bottom of housing 102 is formed by removable nut 106, and this nut 106 allows to change elastomer block 104 under the situation that need not to take off the bar 98 that passes each element 104,106 as shown in figure 11.

In order to apply compression force on bar, bar has another area supported 108, and this another area supported 108 contacts with elastomer block 104, and more clearly relative with the face on housing 102 bottoms of being shelved on of piece face contact.This area supported 108 can be arranged on the strain component 110, and this strain component is installed on the threaded portion 112 of bar 98 in the mode that is threaded.So advantageously make and to be configured for regulating the device of the spacing between two area supporteds 101,108 that are bearing in respectively on the supporting construction and on the frame.This function not only makes can help the placement of blocking element 90 in opening, and can apply the compression prestress of expectation value when screwing strain component 110 to blocking element.

In addition, preferably, make that damping member 104 is merely able to compress on limited crush stroke C, exceed this crush stroke C, structure contacts with rigidity between the frame to stop and continues extruding.This contact for example obtains by making area supported 108 abut against surface 114, and the opening of the housing 102 that holds elastomer block 104 has been defined on surface 114.

Figure 12 illustrates a possible embodiment at each attaching parts that is combined with second damping

member

94,96.

This illustrate bottom surfaces 46 at crosspiece 46 ' on, be provided with and hold for example housing 120 of second damping member 94 of elastomer block form.The bottom of housing 120 is made of removable nut 122, because axle 124 integrates with nut 122, therefore allows for example easily to change elastomer block 94 by turning on nut.

Piece 94 therefore be bearing in the bottom of housing 120 and be bearing in face 56 ' designated surface 126 on.Piece 94 is squeezed between these two supporting powers thus.

In addition, preferably, make second damping member 94 be merely able to compress on limited crush stroke C ', surpass this crush stroke, structure contact to stop with rigidity between the frame and continues to push.This contact for example obtains by making surface 126 abut against surface 128, and the opening of the housing 120 that holds elastomer block 94 has been defined on surface 128.

Therefore, deducibility goes out, and guarantees that first securing device that half hitch structure 22 is assembled in the frame 50 is the element that bears clamp load exclusively.

As mentioned above, first securing device and second securing device are finished by application force recovery pipe link 66.

Certainly, those skilled in the art can carry out various remodeling to the present invention who only is described as non-limiting example.From this respect, should be pointed out that the embodiment that can be applied to all other imagination about described each feature of given embodiment.

Claims

1. the rear portion of an aircraft (1), it comprises:

Fuselage (6), described fuselage define the interior zone (8) of described aircraft;

At least two driving engines (10);

The supporting construction (14) that is used for described driving engine, described supporting construction locates to pass described fuselage at first opening and second opening (18,18), described first opening and second opening are formed in the described fuselage and are distributed on the both sides of vertical mid-plane (P) of described aircraft, and described supporting construction has first and second opposed ends (20,20);

One of them described driving engine is outwards given prominence to and support to described first and second opposed ends of described supporting construction from described fuselage respectively separately on the both sides of described vertical mid-plane; And

Described supporting construction (14) is connected to the securing device of described fuselage (6), and described securing device comprises and described structure is connected to first securing device of first frame (50) that forms described first fuselage opening (18) and described structure is connected to second frame (50) second securing devices that form described second fuselage opening (18);

It is characterized in that,

Described securing device also comprises at least one application force answer pipe link (66), the first end that described application force is replied pipe link is installed on the described supporting construction (14), and the described application force opposed end of replying pipe link is installed in that described fuselage (6) is gone up and spaced apart with described first opening and second opening (18,18).

2. the rear portion of aircraft according to claim 1 is characterized in that, observes along the longitudinal direction (X) of aircraft, and described application force recovers vertical direction (Z) inclination of pipe link (66) with respect to described aircraft.

3. the rear portion of aircraft according to claim 1 and 2 is characterized in that, two application forces is set recovers pipe link (66,66), and described two application forces recover pipe link and arrange symmetrically about the described vertical mid-plane (P) of described aircraft.

4. the rear portion of aircraft according to claim 3, it is characterized in that, described supporting construction (14) forms V-arrangement basically, and described two application forces recovery pipe links (66,66) form together basically with respect to the inverted V-arrangement of the V-arrangement of described supporting construction.

5. according to the rear portion of claim 3 or 4 described aircraft, it is characterized in that, the described opposed end of described two pipe links (66,66) is installed in the same point on the described fuselage (6) basically, and described point belongs to the described vertical mid-plane of described aircraft.

6. according to the rear portion of each described aircraft in the aforementioned claim, it is characterized in that each application force recovers pipe link (66) in the hinged installation in its end.

7. according to the rear portion of each described aircraft in the aforementioned claim, it is characterized in that each application force recovers the top that pipe link (66) is installed in described supporting construction.

8. according to the rear portion of each described aircraft in the aforementioned claim, it is characterized in that at least one application force recovers pipe link (66) and is equipped with syntonizer (150).

9. according to the rear portion of each described aircraft in the aforementioned claim, it is characterized in that, at least two application forces recover pipe links (66) to be arranged to be hinged on the plate (158), described plate itself be hinged on that described supporting construction (14) goes up or described fuselage (6) on.

10. according to the rear portion of each described aircraft in the aforementioned claim, it is characterized in that, described supporting construction (14) is made by the first half hitch structure and the second half hitch structure (22,22) of described first opening that passes described fuselage respectively and second opening (18,18), and the described first half hitch structure and the second half hitch structure are assembled each other and made them to dismantle in described interior zone (8).